Aeroplane-balance.



' G. MEZZATESTA.

AEROPLANE BALANCE.

APPLICATION FILED OCT. 6, 1913 Patent-ea May 18,1915.

3 SHEETSSHEET 1- l lr sa wm G. MEZZATESTA. AEROPLANE B ALANCE.

APPLICATION FILED OCT. 6. I913.

Patented May18,1915.

3 SHEETSSHEET 2.

LTAQ ILSQO G. MEZZATESTA.

AEROPLANE BALANCE.

APPLICATION FILED OCT. 6. 1913.

Patented May 18, 1915.

3 SHEETSSHEET 3 M fil ayar STATEd PATENT @FFFIQE.

GASPAR MEZZATESTA. O1 NEvV YORK, N. Y.

AEROPLANE-BALANCE.

Application filed October 6, 1913.

To all "117207724115 my concern:

lie it known that I, Gnsran hilnzznrns'rn, a subject of the King of Italy, and a resident of the city of New York, borough of Manhattan, county and State of New York, have invented a-new and Improved Aeroplanellalance, of which the following is a full, clear, and exact description.

'1. his invention relates, to improvements in ilOl'OPlilTlC'S. and particularly to means for balancing the aeroplane autmnatically.

The object in. view is to provide an improved structure which may be easily thrown into operation and out of operation, and when in operation to automatically maintain the aeroplane in the course being -followed.

Another object of the invention is to provide a controlling device for the balancing members of the aeroplane and the elevation plane, which includes air controlled pistons for operating the balancing members and rudder, which pistons are in turn controlled by a gravity actuated valve so that when the aeroplane tilts or pitches the air pressure will be varied, and the pistons will operate for automatically shifting the pq; sition of the balancing planes or of the rudder.

A still further object of the invention is to provide pressure operated means for con trolling the various movable planes, the pressure operated means being automatically set in motion by a gravity actuated valve so that any movement out of the straight course will cause a readjustment of the planes.

In carrying out the obj ect of the invention it is designed to apply the device to any desired form of aeroplane so as to operate the balancing members, and also the elevation members thereof automatically. In ar-' ranging the device in position means are provided for switching on and 0d the device so that when switched off the aeroplane may be operated manually in the usual mannor of that particular make, but when the.

device is switched on the same automatically controls the balancing device of the aeroplane as well as the steering features so as to maintain the aeroplane in its original course, and to return it to said course when moved therefrom by any particular action of the atmosphere. In arranging the device formed according to the present invention on an aeroplane, connecting members of any Specification of Letters Patent.

Patented May 18, lltl'i Serial No. 793,641.

desired kind are com'iected with the rudder, and with the baiancinf); planes, and also with movable mranbers, which in turn are connected with the pistons of the automatic balancing device. These pistons are arranged in suitable cylinders, and are operated by fluid pressure, as for instance com pressed air, so that when the aeroplane is moving along in a proper horizontal position the pistons will be stationary, but it the aeroplane should pitch or tilt to one side the cylinder affected would be supplied with air so as to operate the proper plane. A gravity actuated valve is provided for the cvlinders controlling the tilting planes or balancing planes, and a second gravity aetuated valve is provided for the rudder or steering plane at the rear so that the same may be operated when the aeroplane pitches.

In the accompanying drawings-Figure 1 is a side view of an aeroplane in diagram, an eml'iodiment of the invention being shown applied thereto; Fi is a front view of the structure shown in Fig. 1; Fig. 3 is an enlarged side view of one of the gravity actuated valves; Fig. l is a diagram showing the arrangement of the pistons, valves and associated parts for automatically shifting the position of the planes; Fig. 5 is a dia gram showing the upper part of the structure disclosed in Fig. 4:, the valve being shown tilted in one direction; Fig. 6 is a view similar to Fig. 5 except that the valve is shown tilted in the opposite direction; Fig. 7 is an enlarged detailed fragmentary plan view of the mechanism for throwing 1n and out the automatic controlling de vices. I

Referring to the accompanying drawings by numeral 1 indicates an aeroplane of any desired kind which is provided with balancing planes 2 and 3 of any desired kind, the particular structure of the aeroplane and the balancing planes not forming any part ofthe present invention. The aeroplane is also provided with a rear steering plane 4. In the ordinary manipulation the planes 2, 3 and 4 are actuated by the operator for causing the aeroplane to move up ordown, or from one side to the other. Also, these planes are moved by the operator for properly balancing and directing the aeroplane in a'straight course. The automatic means forming the present invention is designed to cause the aeroplane to move in a straight line after having been started on such a course that the peratdr needno p ypbint towardt eearth and thus move ialve any attention to the balancing or steering'ofy 20 as the aeroplane -is tilted. As valve 20 the aeroplane when he desireson ly to move is comparatively'isma ll and only a small in a direct line. In order to do this any tiltpower is needed for actuating the same ing or pitching of the aeroplane must be '=-wei-ght30"is comparatively small and weighs resisted and the various planes 2,- 3 andfl preferably only a few pounds. When the must be adj-ustedupon eachmovement-ofthe valve 20 moves from the positiori 'sliown in aeroplane to'bring the aeroplane-backto' its Fig.4 to thatshqwn in Fig. 5 air passes original course. In accomplishing this refrom pipe 25" into valve 20 and through sult cylinders Sand-Gare provided forplane passageway31 to passageway132,-and from 75 4: and cylinders 7 and? provided for the passageway 32;.into pipe 18. From pipe 18' planes 2 and 3. Theseg cylinders are .detheair passesinto.cylinderfi and moves .p issigned toreceiveair pressure or any desired ton 10 upwardly from cable-pulling mem pressure from tank 8, and .through proper, bars .15. Simultaneously with =the admismechanism hereinafter fully I described to sion, of compressed-air into cylinder 6 thego; automatically elevate or depresss thefresp ec; compressed air in. cylinder 5 will be exhausttive planes .just mentioned when the, equied through pipe 16,,- passag'eway33 and ex librium of. the aeroplane has been disturbedhaust-pipe 3 1. i In case the -aeroplane,should I The'cylinders are made alike, and Cylinders tilt ,to theeo'ppositeg, position valve will, 20 5 and 6 are similar to cylinders 7 and/7; but assume the positionshown in Fig.5 and-the-:%g5; arranged to control the rear plane iinstead: pistons will make .ad reverse, movement, as of-the side planes? and 3.; In Figs. 4, 5 and shown in Fig- 6,. Itis of course understood 6adiagramofthestructureof thesecylinders that valve 21' is, closed,when;.-val;ve 24 is'w- "'and-howthey operate is disclosed.- Referopened sothat the pressure;"passing from i ring in detaiLto these figuresit .willbe ob-l valve 20 cannotescape-until' afteraithasen -go served that the cylinders 5 and 6 carry pistered the respective cylinders, and even'theni tons 9and lO' which are provided with pis-. ,cannot escape until thezvalve has beemtiltton rodsll and12 having cross bars 13 and ed, as shown in Figs. 5 and;.6 This valive20 14. Gonnected'with the cross bars 13 and is arranged tocontrolthe pressure .in- -.cy-1in.--

14. are cables or other power transmitting ders 5 and 6, and a valve20 similar to valve-: 5

members 15. Thepower transmitting nieim. I 20 is arranged to control-the pressure in the, bers 15 are connected withtheusual plane cylinders-7 and 7. v'I -he,-valves; 20 and} 20/ controlling cables so that/when. the pistons, .areidentical in structure,butuareset-so asto 'are operated, the regular. cables are also 1 operate differently, namely-,yalve20 is de- 1 55 operated for'va'rying the position of. theresigned, to swing freely; from front to-rears spe'ctive planes Connected with the lower in case the aeroplaneishonld .pitch, bu'tfwilli end of cylinder 5 are pipes 16 and 17, while notmove in case the-aeroplane-should toss; connected with'the lower end of cylinder 6: or tilt sidewise. However, valve 20, is.ar;--= are pipeslS and 19. Pipes 16 and 18 extend I ranged to move-freely lateral-ly in. a pivotal upwardly andare connected withhousing 19- direction so as to swingiwheii the aeroplane ,2105; of valve v2,0. Pipes I7fand19fextend to a: tosses ortilts si'dewise. In this wayther'esmanually controlled valve 21 having pas- SpQQtiVQ. VQ,1VQ, Wi11properly p t th e sageways 22 and 23 extending therethrough so that a single valve 21 mayopenor close 1 correctly.

4 .5 both of the pipes '17 and 19. Associated Whenthe automatic balancing de i g -i p with valve21/is valve'24interposed in pipe in operation valves 21 and 24 are set as 25. Valves 21 and 24 are provided with op-v shown in 7 However, in case it should crating levers 26 and2 Z, andwith-aconnectbe desired to operate. the various-planes in- 'ing link 28, whereby when lever-27 lsactudependently of -the..au tomatic' means, theated both of the valvesiwill-be moved. The..,- automatic means may benswitched,ioff ibya lia tank 8 ,containingthe compressed-air iscon- .merely .operatingdever, 2,7, soas to-preventtinually in communication with p,ipe';25,,,and passage of-air .fnom, {pipe -25 to= 25,- andto I when valve 2i is openedair is supplie'dgtoy'jallow the freeescape of'air from ipipes 17- pipe 25", :whic'h air passes upwardly tovalve and; 18, Iniorder. to,a"ccomplish;this result 1 56 20.. When the planes arein their :normal. 'when ,valve,,21-is open-and valve. 24L; close.d, .120-

position the valve 20 will bein the position. as shown in Fig. 4,the pressureis exhausted shown ii'1 Fig 4.1 If'the'aeroplane should ;-from. the cylinders, through pipes; 17.and 19', tilt in onedirection the valve 20.would move ,and. valv,e 214, so that manual operation of I "to the position shown in Fig. 5 and iitilt- .the,,stabilizers.is not;-resisted by the pistons, e 60 ed in the vopposite direction would moveto 9 and 10. a 1,, 25. the position 'shown -in Fig, 6 Valve20 is 'Ihe connecting members ,15 sassociated provided with an operating arm orlever 29. wi th the cy1i nders-5and6 are connected tor h sllfl e a Weigh 3 he weightBO, theirudderimanipulating'cables .;35.. and-;-36? is Qt'cours'eactefd upon by 'gray1ty,, and, will. (Fig.1). ,It;willbe observedthatvwhen barll cause lever' forfarm 29 to continually,113-,is pullediplane eilwill be moved-in onea'iso rect'planes when the aeroplanemoves in r direction, andwhen bar 14 is pulledplane 4 will be moved in the opposite direction so as to cause the aeroplane to rise or descend. When either of the cylinders. 7 or 7 is operated the bar 87 (Fig. 2) is moved, and bar 37 is rigidly secured to shaft 38, which shaft carries a sprocket wheel 39 over which the controlling members 40 and 41 are passed. As the sprocket wheel 39 is moved one way or the other the planes 2 and 3 will be tilted. It is of course evident that other connecting means could be provided for the pistons in cylinders 7 and 7 without departing from the spirit of the invention provided the movement of the istons is properly communicated to the si e balancing planes. The side balancing planes may be part of the main plane and be warped, or may be separate members, and tilted when manipulating the aeroplane, the de-- tailed structure of these planes and the means for actuating the same not forming any part of the invention. It is therefore to be noted that applicants device resides in the automatic means which operates the controlling members on an aeroplane, which automatic means may be at any time thrown into operation or thrown out of operation by a movement of the lever 27. When the aeroplane tilts sidewise the valve will be moved by its pendulum or weight 30, and lever 29, so as to admit pressure into one of the cylinders 7 or 7 and exhaust pressure from the opposite cylinder so that one of the planes or both planes 2 and 3 may be operated for bringing the aeroplane back to a horizontal position. lVhen the aeroplane again reaches a horizontal position the air is again admitted into both cylinders so that the same are evenly balanced. When the aeroplane pitches or attempts to go up or down at an angle valve 20 is moved and bars 13 and 14 associated with the cylinders 5 and 6 are actuated for properly manipulating plane 4.

It will be obseri'ed from the way the air under pressure is admitted to the various cylinders that the pistons thereof automatically move whenever the aeroplane is out of its ordinary horizontal position. As soon as the aeroplane assumes its horizontal position the automatic means is balanced. As the automatic means holds the aeroplane in a straight course and continually in a horizontal position the same must be thrown out when it is desired to turn or to rise or descend. This may be easily done by moving lever 27 to the position shown in Fig. 4.

The automatic means is then deprived of air under pressure and the various steering members of the aeroplane may be operate in the usual manner by the usual operating appliances. any kind, as for instance a steering wheel 40 secured to a suitable shaft 41, which shaft carries a sprocketwheel. 42. The shaft 41 is mounted upon a support 43 pivotally held in place by a suitable journal member 44 so that wheel 40 and associated parts maybe swung rearwardly and forwardly at will for manually moving the cables and 36 so as to vary the position of the plane 4. When it is designed to manipulate the balancing planes 2 and 3, wheel is rotated or partially rotated in the desired direction, whereupon the chain 45 will be moved. The ends of chain 45 (Fig. 2) are connected with bar 37 through suitable cables 46 and 47 so that a rotary movement of the sprocket 42 will cause a corresponding movement of bar 37, whereupon the cables connecting the same with planes 2 and 3 will be moved. It is to be noted that the-manually operated means are only actuated by the operator when the automatic control is turned out of operation.

What I claim is In an aeroplane balancing device, the combination of the usual balancing and steering planes of an aeroplane, of mechanism for actuating said planes, said mechanism comprising a pair of reciprocating members for the plane controlling the lateral balance of the aeroplane, a pair of reciprocating members for actuating the plane controlling the pitching of the aeroplane, means for supplying power to all of said reciprocating members, a pair of gravity actuated power controlling members for turning on and off the power as the aeroplane tosses or pitches, and manually controlled means for disconnecting the power from all of said reciprocating members, said manually controlled means comprising a pairof valves, a connection between said valves forcausing the same to act simultaneously, whereby one is closed as the other is opened, and means for moving said connection.

In testimony whereof I have signed my name to this specification in the presenceof two subscribing witnesses.

GASPAR M'EZZATESTA. lVitnesses:

A. L. KITQHIN, PHILIP D. RoLLHAus.

These appliances may be of 

